EP4212777B1 - Brennkammerdüse - Google Patents

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Publication number
EP4212777B1
EP4212777B1 EP23150043.0A EP23150043A EP4212777B1 EP 4212777 B1 EP4212777 B1 EP 4212777B1 EP 23150043 A EP23150043 A EP 23150043A EP 4212777 B1 EP4212777 B1 EP 4212777B1
Authority
EP
European Patent Office
Prior art keywords
fuel
tube
swirling
disposed
swirler
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Active
Application number
EP23150043.0A
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English (en)
French (fr)
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EP4212777A1 (de
Inventor
Borys Shershnyov
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Doosan Enerbility Co Ltd
Original Assignee
Doosan Enerbility Co Ltd
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Application filed by Doosan Enerbility Co Ltd filed Critical Doosan Enerbility Co Ltd
Publication of EP4212777A1 publication Critical patent/EP4212777A1/de
Application granted granted Critical
Publication of EP4212777B1 publication Critical patent/EP4212777B1/de
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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F23R3/30—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply comprising fuel prevapourising devices
    • F23R3/32—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply comprising fuel prevapourising devices being tubular
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F23R3/286—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply having fuel-air premixing devices
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/22—Fuel supply systems
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D14/00—Burners for combustion of a gas, e.g. of a gas stored under pressure as a liquid
    • F23D14/46—Details, e.g. noise reduction means
    • F23D14/62—Mixing devices; Mixing tubes
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/04—Air inlet arrangements
    • F23R3/10—Air inlet arrangements for primary air
    • F23R3/12—Air inlet arrangements for primary air inducing a vortex
    • F23R3/14—Air inlet arrangements for primary air inducing a vortex by using swirl vanes
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/16—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration with devices inside the flame tube or the combustion chamber to influence the air or gas flow
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/35—Combustors or associated equipment

Definitions

  • the present invention relates to a combustor nozzle and, more particularly, to a combustor nozzle including a plurality of tubes with swirlers, and a combustor.
  • a gas turbine is a combustion engine in which a mixture of air compressed by a compressor and fuel is combusted to produce a high temperature gas, which drives a turbine.
  • the gas turbine is used to drive electric generators, aircraft, ships, trains, or the like.
  • the gas turbine generally includes a compressor, a combustor, and a turbine.
  • the compressor serves to intake external air, compress the air, and transfer the compressed air to the combustor.
  • the compressed air compressed by the compressor has a high temperature and a high pressure.
  • the combustor serves to mix compressed air from the compressor and fuel and combust the mixture of compressed air and fuel to produce combustion gases, which are discharged to the gas turbine.
  • the combustion gases drive turbine blades in the turbine to produce power.
  • the power generated through the above processes is applied to a variety of fields such as generation of electricity, driving of mechanical units, etc.
  • Fuel is injected through nozzles disposed in respective combustors, wherein the fuel includes gaseous fuel and liquid fuel.
  • the fuel includes gaseous fuel and liquid fuel.
  • US 2019 / 0 360 697 A1 discloses a fuel injector for a gas turbine comprising a fuel supply pipe, a plurality of premix tubes, an upstream side plate, a downstream side plate, and an outer wall.
  • the premix tubes extend through the plenum and include fuel through holes to communicate the premix tubes with the plenum.
  • a guide part is provided at an upstream end of each premix tube positioned upstream the upstream side plate.
  • the guide part includes ribs protruding inwardly from the circumference of tube to function as a swirler.
  • an objective of the present invention is to provide a combustor nozzle capable of minimize nitrogen oxide generation and increasing flame stability by improving the mixing characteristics of fuel and air, a combustor, and a gas turbine including the same.
  • the present invention provides a combustor nozzle in accordance with claim 1 and a combustor in accordance with claim 15.
  • a combustor nozzle including a nozzle module.
  • the nozzle module includes a fuel supply pipe, a fuel plenum, an air inlet, a plurality of tubes, and a swirler.
  • the fuel supply pipe supplies fuel from the front side to the rear side.
  • the fuel plenum has an internal fuel flow path through which the fuel flows and communicating with the fuel supply pipe.
  • the air inlet is formed in front of the fuel plenum.
  • the tube is disposed through a rear side of the fuel plenum, wherein a front end thereof communicates with the air inlet, and a fuel port communicating with the fuel flow path is formed on a lateral side thereof.
  • the swirler is provided with a plurality of swirling guides disposed obliquely in axial and circumferential directions on an inner circumferential surface of each of the plurality of tubes to swirl a fluid, with a central portion thereof opened when viewed from the axial direction of the tube.
  • the swirler may have the central portion opened in a circular shape when viewed from the axial direction of the tube.
  • the plurality of swirling guides may be disposed in a continuous annular shape when viewed from the axial direction of the tube.
  • the plurality of swirling guides include a straight part extending along the axial direction of the tube and a swirling part extending in the axial and circumferential directions of the tube from a rear end of the straight part.
  • the swirling part may be formed to be inclined in a curved form on the tube.
  • the length of the swirling part in the axial direction of the tube may be formed longer than that of the straight part.
  • a front end of the straight part may be provided with an inclined portion inclined toward the rear side as the inclined portion extends from the outside toward the inside of the tube.
  • the fuel port may include a first fuel port passing through the tube and the plurality of swirling guides and disposed on the plurality of swirling guides.
  • the fuel port may include a first fuel port passing through the tube and the plurality of swirling guides and disposed on the straight part.
  • the fuel port may include a second fuel port passing through the tube and disposed between the plurality of swirling guides.
  • the fuel port may include a second fuel port passing through the tube and disposed between the straight parts.
  • the fuel port may include a second fuel port passing through the tube and disposed between the plurality of swirling parts.
  • the swirler may be disposed at the front end of the tube.
  • the fuel port may include a third fuel port passing through the tube and disposed at a front side of the swirler.
  • the fuel port may include a fourth fuel port passing through the tube and disposed at a rear side of the swirler.
  • a combustor including a combustor nozzle, and a duct assembly.
  • the combustor nozzle includes a nozzle module.
  • the duct assembly is coupled to one side of the combustor nozzle.
  • fuel and air are combusted, and the combustion gases are delivered to a turbine.
  • the nozzle module includes a fuel supply pipe, a fuel plenum, an air inlet, a plurality of tubes, and a swirler.
  • the fuel supply pipe supplies fuel from the front side to the rear side.
  • the fuel plenum has an internal fuel flow path through which the fuel flows, the fuel flow path communicating with the fuel supply pipe.
  • the air inlet is formed in front of the fuel plenum.
  • the tube is disposed through a rear side of the fuel plenum, wherein a front end thereof communicates with the air inlet, and a fuel port communicating with the fuel flow path is formed on a lateral side thereof.
  • the swirler is provided with a plurality of swirling guides disposed obliquely in axial and circumferential directions on an inner circumferential surface of each of the plurality of tubes to swirl a fluid, with a central portion thereof opened when viewed from the axial direction of the tube.
  • the swirler may have the central portion opened in a circular shape when viewed from the axial direction of the tube.
  • the plurality of swirling guides may include a straight part extending along the axial direction of the tube and a swirling part extending in the axial and circumferential directions of the tube from a rear end of the straight part.
  • the fuel port may include a first fuel port passing through the tube and the plurality of swirling guides and disposed on the plurality of swirling guides.
  • a gas turbine including a compressor, a combustor, and a turbine.
  • the compressor compresses air introduced from the outside.
  • the combustor mixes the air compressed in the compressor and fuel and combusts an air-fuel mixture.
  • the turbine includes a plurality of turbine blades to be rotated by combustion gases combusted in the combustor.
  • the combustor includes a combustor nozzle and a duct assembly.
  • the nozzle includes a nozzle module.
  • the duct assembly is coupled to one side of the combustor nozzle. In the duct assembly, the fuel and the air are combusted, and the combustion gases are delivered to a turbine.
  • the nozzle module includes a fuel supply pipe, a fuel plenum, an air inlet, a plurality of tubes, and a swirler.
  • the fuel supply pipe supplies fuel from the front side to the rear side.
  • the fuel plenum has an internal fuel flow path through which the fuel flows, the fuel flow path communicating with the fuel supply pipe.
  • the air inlet is formed in front of the fuel plenum.
  • the tube is disposed through a rear side of the fuel plenum, wherein a front end thereof communicates with the air inlet, and a fuel port communicating with the fuel flow path is formed on a lateral side thereof.
  • the swirler is provided with a plurality of swirling guides disposed obliquely in axial and circumferential directions on an inner circumferential surface of the plurality of tubes to swirl a fluid, with a central portion thereof opened when viewed from the axial direction of the tube.
  • the plurality of tubes with swirlers are provided so that the mixing characteristics of fuel and air are improved and the generation of nitrogen oxide is minimized to increase flame stability.
  • FIG. 1 is a view illustrating the interior of a gas turbine
  • FIG. 2 is a view illustrating a combustor of FIG. 1 .
  • thermodynamic cycle of a gas turbine 1000 follows a Brayton cycle.
  • the Brayton cycle consists of four thermodynamic processes: isentropic compression (adiabatic compression), isobaric combustion, isentropic expansion (adiabatic expansion) and isobaric heat ejection. That is, in the Brayton cycle, atmospheric air is sucked and compressed into high pressure air, mixed gas of fuel and compressed air is combusted at constant pressure to discharge heat energy, heat energy of hot expanded combustion gas is converted into kinetic energy, and exhaust gases containing remaining heat energy is discharged to the outside. That is, gases undergo four thermodynamic processes: compression, heating, expansion, and heat ejection.
  • the gas turbine 1000 employing the Brayton cycle includes a compressor 1100, a combustor 1200, and a turbine 1300.
  • a compressor 1100 As illustrated in FIG. 1 , the gas turbine 1000 employing the Brayton cycle includes a compressor 1100, a combustor 1200, and a turbine 1300.
  • the present invention may be widely applied to other turbine engines similar to the gas turbine 1000 illustrated in FIG. 1 .
  • the compressor 1100 of the gas turbine 1000 may suck and compress air.
  • the compressor 1100 may serve both to supply the compressed air by compressor blades 1130 to a combustor 1200 and to supply the cooling air to a high temperature region of the gas turbine 1000.
  • the sucked air undergoes an adiabatic compression process in the compressor 1100, the air passing through the compressor 1100 has increased pressure and temperature.
  • the compressor 1100 is usually designed as a centrifugal compressor or an axial compressor, and the centrifugal compressor is applied to a small-scale gas turbine, whereas a multi-stage axial compressor is applied to a large-scale gas turbine 1000 illustrated in FIG. 1 since the large-scale gas turbine 1000 is required to compress a large amount of air.
  • the compressor blades 1130 of the compressor 1100 rotate according to the rotation of the rotor disks to compress the introduced air and move the compressed air to the compressor vanes 1140 on the rear stage. As the air passes through the compressor blades 1130 formed in multiple stages, the air is compressed to a higher pressure.
  • the compressor vanes 1140 are mounted inside the housing 1150 in stages.
  • the compressor vanes 1140 guide the compressed air moved from the front side compressor blades 1130 toward the rear-side compressor blades 1130.
  • at least some of the compressor vanes 1140 may be mounted so as to be rotatable within a predetermined range for adjustment of an air inflow, or the like.
  • the compressor 1100 may be driven using a portion of the power output from the turbine 1300. To this end, as illustrated in FIG. 1 , the rotary shaft of the compressor 1100 and the rotary shaft of the turbine 1300 may be directly connected. In the case of the large-scale gas turbine 1000, almost half of the output produced by the turbine 1300 may be consumed to drive the compressor 1100. Accordingly, improving the efficiency of the compressor 1100 has a direct effect on improving the overall efficiency of the gas turbine 1000.
  • the turbine 1300 includes a rotor disk 1310 and a plurality of turbine blades and turbine vanes radially disposed on the rotor disk 1310.
  • the rotor disk 1310 has a substantially disk shape on which a plurality of grooves is formed.
  • the grooves are formed to have curved surfaces, and turbine blades and turbine vanes are inserted into the grooves.
  • the turbine vanes are fixed against rotation and guide a flow of combustion gases through the turbine blades.
  • the turbine blades are rotated by combustion gases to generate rotational force.
  • the combustor 1200 serves to mix the compressed air supplied from an outlet of the compressor 1100 with fuel and combust the mixture at constant pressure to produce hot combustion gases.
  • FIG. 2 illustrates an example of the combustor 1200 provided in the gas turbine 1000.
  • the combustor 1200 may include a combustor casing 1210, nozzles 1220, and a duct assembly 1240.
  • the combustor casing 1210 may have a substantially circular cylindrical shape in which the nozzles 1220 are surrounded.
  • the nozzle 1220 is disposed downstream of the compressor 1100 and may be disposed along the annular combustor casing 1210.
  • Each nozzle 1220 is provided with at least one nozzle module 1400, through which fuel and air are mixed in an appropriate ratio and injected to achieve a suitable state for combustion.
  • the gas turbine 1000 may use a gas fuel, in particular, a fuel containing hydrogen.
  • the fuel may include a hydrogen fuel alone or a fuel containing hydrogen and natural gas.
  • the duct assembly is provided to connect the nozzles 1220 and the turbine 1300 so that the hot combustion gas flows therethrough to heat the duct assembly, whereas the compressed air flows towards the nozzles 1220 along an outer surface of the duct assembly 1240, thereby properly cooling the heated duct assembly 1240.
  • the duct assembly 1240 may include a liner 1241 and a transition piece 1242, and a flow sleeve 1243.
  • the duct assembly 1240 has a double structure in which the flow sleeve 1243 surrounds the outside of the liner 1241 and the transition piece 1242, so that compressed air penetrates into an annular space inside the flow sleeve 1243 to cool the liner 1241 and the transition piece 1242.
  • the liner 1241 is a tube member connected to the nozzles 1220 of the combustor 1200, wherein an internal space of the liner 1241 defines the combustion chamber 1230.
  • a longitudinal one side of the liner 1241 is coupled to the nozzle 1220, and the other side of the liner 1241 is coupled to the transition piece 1242.
  • the transition piece 1242 is connected an inlet of the turbine 1300 to guide the hot combustion gas toward the turbine 1300.
  • a longitudinal one side of the transition piece 1242 is coupled to the liner 1241, and the other side of the transition piece 1242 is coupled to the turbine 1300.
  • the flow sleeve 1243 serves to protect the liner 1241 and the transition piece 1242 while avoiding direct exhaust of hot air to the outside.
  • FIG. 3 is a longitudinal cross-sectional view illustrating a state in which a nozzle module is coupled to a tube assembly in a combustor nozzle according to a first embodiment of the present invention
  • FIG. 4 is a perspective view separately illustrating a tube and a swirler in FIG. 3 in an enlarged fashion
  • FIG. 5 is a front view separately illustrating a tube and a swirler in FIG. 3 in an enlarged fashion
  • FIG. 6 schematically illustrates distribution of a flow velocity formed around the swirler according to the first embodiment of the present invention.
  • the combustor nozzle 1220 includes at least one nozzle module 1400.
  • the nozzle module 1400 includes a fuel supply pipe 1420 and a tube assembly 1500, which includes swirlers 1530.
  • the fuel supply pipe 1420 is a tubular member for supplying fuel from the front side to the rear side.
  • An internal fuel flow path through which fuel flows is formed in the fuel supply pipe 1420.
  • a flange 1410 may be disposed at a front end of the fuel supply pipe 1420, and fuel may flow into the fuel supply pipe 1420 through the flange 1410.
  • the tube assembly 1500 includes a fuel plenum 1510, a tube 1520, and a swirler 1530.
  • the fuel plenum 1510 may have a substantially cylindrical shape and may be disposed to surround at least a portion of the rear end side of the fuel supply pipe 1420.
  • An open air inlet 1511 is formed at a front end of the fuel plenum 1510 to allow air to be introduced therethrough.
  • a first support plate 1512a may be disposed at a rear end of the fuel plenum 1510, and a second support plate 1512b may also be disposed between the rear end of the fuel plenum 1510 and the air inlet 1511.
  • the fuel supply pipe 1420 may be disposed so as to pass through the second support plate 1512b disposed between the rear end of the fuel plenum 1510 and the air inlet 1511, and be inserted up to the first support plate 1512a disposed at the rear end of the fuel plenum.
  • a space is formed between the first and second support plates 1512b disposed in the fuel plenum 1510, and the space communicates with the fuel supply pipe 1420. Accordingly, a fuel flow path 1513 through which fuel flows is formed in the space.
  • the plurality of tubes 1520 are disposed in the fuel plenum 1510 in the form of a bundle.
  • the tube 1520 may be inserted up to the second support plate 1512b through the first support plate 1512a disposed on the rear end side of the fuel plenum 1510. Accordingly, each tube 1520 is inserted into the fuel flow path 1513.
  • the tube 1520 may be supported by the first and second support plates 1512b. Meanwhile, a gap between the tube 1520 and the first/second support plate 1512a/1512b may be sealed to prevent fuel leakage to the outside from the fuel flow path.
  • Air may be introduced through the front end of the tubes 1520.
  • the air introduced through the air inlet 1511 of the fuel plenum 1510 may flow in the fuel plenum 1510 and flow into respective front ends of the tubes 1520.
  • the introduced air may pass through the tubes 1520 and be discharged through the rear ends of the tubes 1520.
  • the rear ends of the tubes 1520 communicate with a combustion chamber 1230. Accordingly, air and fuel are mixed in the tubes 1520, and the mixed fluid of the air and the fuel is discharged through the rear ends of the tubes 1520 and injected into the combustion chamber 1230.
  • a fuel port is formed in the tube 1520.
  • the fuel port may be formed on a lateral side of the tube 1520.
  • the fuel port communicates with the fuel flow path 1513 of the fuel plenum 1510, as well as with an inner flow path of the tube 1520. Accordingly, the fuel flowing in the fuel flow path 1513 may be introduced into the tube 1520 through the fuel port. Since air and fuel flow together in the tube 1520, the air and the fuel are mixed with each other in the tube 1520.
  • a swirler 1530 is disposed inside the tube 1520.
  • the swirler 1530 is configured to swirl a flow of fluid flowing in the tube 1520, that is, a flow of air and fuel.
  • the swirler 1530 includes a swirling guide 1531 for swirling the fluid.
  • a plurality of swirling guides 1531 are provided.
  • the swirling guide 1531 ise disposed on an inner circumferential surface of the tube 1520.
  • a central portion 1530a of the swirler 1530 is open. Accordingly, when a fluid passes through the swirler 1530 in the tube 1520, a flow of the fluid may be divided into a linear flow flowing in a straight direction and a swirling flow flowing in a swirling direction.
  • the fluid passing through the central opening of the swirler 1530 is the linear flow and flows in a straight direction in a direction toward the rear end of the tubes 1520 without being swirled.
  • the fluid not passing through the open central portion 1530a of the swirler 1530 is a swirling flow and swirls during passing through the swirling guide 1531 of the swirler 1530.
  • a linear flow may be formed in the center, and a swirling flow may be formed around and surrounding the linear flow.
  • the linear flow and the swirling flow are not completely separated from each other, but may be formed such that at least a part of the swirling flow is drawn to the linear flow. Accordingly, as the linear flow and the swirling flow are formed together, it is possible to advantageously improve the mixing characteristics of air and fuel while minimizing pressure loss of the air-fuel mixture.
  • the central portion 1530a of the swirler 1530 may be opened in a circular shape.
  • the linear flow may be formed in a circular cross section when viewed in the axial direction of the tube 1520.
  • the swirling guides 1531 when the tube 1520 and the swirler 1530 are viewed in the axial direction of the tube 1520, the swirling guides 1531 may be arranged in an annular shape. At this time, the swirling guides 1531 may be arranged in a continuous annular shape. When viewed in the axial direction, the swirling guides 1531 adjacent to each other may be disposed to overlap each other. In this case, a portion except the central portion 1530a of the swirler 1530 is occupied by the swirling guides 1531, and accordingly, a swirling flow may entirely surround the outer circumference of a linear flow.
  • the swirling guide 1531 includes a straight part 1532 and a swirling part 1533.
  • the straight part 1532 extends long and straight along the axial direction of the tube 1520.
  • the straight part 1532 may be formed to protrude from the inner circumferential surface of the tube 1520 toward the inside of the tube 1520 and extend in the longitudinal direction, which is the axial direction of the tube 1520.
  • the straight part 1532 may be disposed on the front side of the swirling guide 1531.
  • the straight part 1532 is configured to guide fluid flowing into the swirler 1530 in the axial direction of the tube 1520.
  • the straight part 1532 minimizes pressure loss at the swirling guide 1531 because the straight part guides fluid in the axial direction before the fluid passes through the swirling part 1533.
  • the swirling part 1533 is disposed on the rear side of the straight part 1532.
  • the swirling part 1533 is formed to extend from the rear end of the straight part 1532.
  • the swirling part 1533 may protrude from the inner circumferential surface of the tube 1520 toward the inside of the tube 1520.
  • the swirling part 1533 extends in the axial and circumferential directions of the tube 1520. That is, the swirling part 1533 may be formed to be inclined in a direction between the axial direction and the circumferential direction.
  • the swirling part 1533 is configured to swirl fluid that has passed through the straight part 1532.
  • the swirling part 1533 may be formed to be inclined in the form of a curve. According to an embodiment, the swirling part 1533 may be formed to be inclined in the axial direction and the circumferential direction of the tube 1520 such that the swirling part is convex or concave toward the front or rear end of the tube 1520. In this case, it is possible to effectively swirl fluid passing through the swirling part 1533 while reducing the flow resistance of the fluid. In addition, a portion where the swirling part 1533 and the straight part 1532 meet may be formed to be gently, gradually curving and continuously connected to each other. In this case, it is possible to reduce the flow resistance of fluid flowing into the swirling part 1533.
  • the length L2 of the swirling part 1533 may be formed to be longer than the length L1 of the straight part 1532.
  • the main purpose of the swirling guide 1531 is to swirl fluid. Therefore, if the length L1 of the straight part 1532 is formed shorter than the length L2 of the swirling part 1533, there is an advantage that the entire size of the swirler 1530 can be manufactured compactly while effectively swirling the fluid.
  • the inclined portion 1534 may be formed on the straight part 1532 of the swirling guide 1531.
  • the inclined portion 1534 may be formed at the front end of the straight part 1532.
  • the inclined portion 1534 may be inclined backward toward the inside of the tube 1520. Since the straight part 1532 is formed to protrude from the inner circumferential surface of the tube 1520 toward the inside of the tube 1520, when fluid flows into the straight part 1532, the flow resistance at the front end of the straight part 1532 becomes large. At this time, if the inclined portion 1534 is disposed on the straight part 1532, it is possible to reduce the flow resistance of the fluid flowing into the straight part 1532.
  • the fuel port may include a first fuel port 1521.
  • the first fuel port 1521 is a fuel port disposed on the swirling guide 1531.
  • the first fuel port 1521 may be formed at an inner end of the tube 1520 of the swirling guide 1531, or the first fuel port 1521 may be formed on the lateral side of the swirling guide 1531.
  • the first fuel port 1521 is formed through the tube 1520 and the swirling guide 1531. Accordingly, the fuel in the fuel flow path 1513 of the fuel plenum 1510 may pass through the first fuel port 1521, and injected from the swirling guide 1531.
  • fuel may be directly injected into the fluid flowing in a linear form or a swirling form.
  • the first fuel port 1521 may be formed in the straight part 1532 or the swirling part 1533 of the swirling guide 1531. According to an embodiment, if the first fuel port 1521 is disposed at an inner end of the swirling guide 1531, the fuel is directly injected into the fluid flowing in a linear from. If the first fuel port 1521 is disposed on the lateral side of the swirling guide 1531, the fuel is injected into the fluid flowing in a swirling form.
  • the first fuel port 1521 may be formed in the straight part 1532, the fuel may be directly injected as soon as the fluid flows into the swirler 1530.
  • the first fuel port 1521 may be disposed in the inclined portion 1534 of the straight part 1532.
  • a flow of the fuel injected from the first fuel port 1521 may be divided into a linear flow and a swirling flow.
  • a part of the flow of the fuel injected from the first fuel port 1521 may join in the linear flow while another part of the flow of the fuel injected from the first fuel port 1521 may join in the swirling flow.
  • the swirler 1530 may be disposed at the front end of the tube 1520.
  • the front end of the tube 1520 is used to refer to not only the front end terminal of the tube 1520 itself, but also refers to the front end of the tube 1520 and its surroundings.
  • the swirling guide 1531 of the swirler 1530 may be in contact with the front end of the tube 1520, or may be disposed slightly spaced apart therefrom while still being disposed at the front end of the tube 1520.
  • FIG. 6 schematically illustrates a flow rate of fluid around the swirler 1530.
  • the flow rate before passing through the swirler 1530 is a first flow rate V1
  • the flow rate of a linear flow after passing through the swirler 1530 is a second flow rate V2
  • the flow rate of a swirling flow after passing the swirler 1530 is a third flow rate V3.
  • the second flow rate V2 is a fastest flow rate.
  • a flow cross-sectional area decreases in general, and, the flow is converted into a linear flow and accordingly, the flow rate is increased from the first flow rate V1 to the second flow rate V2.
  • the third flow rate V3 of the swirling flow is larger than the first flow rate V1, but smaller than the second flow rate V2. Since the fluid swirls due to the swirling guide 1531 and so the flow rate decreases, due to the interaction with the linear flow, which is the second flow rate V2, a flow rate of the swirling flow is greater than the first flow rate V1.
  • FIG. 7 is a perspective view separately illustrating a tube and a swirler of a nozzle according to a second embodiment of the present invention in an enlarged fashion.
  • a combustor nozzle 1220 according to a second embodiment of the present invention will be described in detail with reference to FIG. 7 . Since the combustor nozzle 1220 according to the second embodiment of the present invention is the same as the combustor nozzle 1220 according to the first embodiment of the present invention, except for a second fuel port 1522, a redundant description thereof will be omitted.
  • the fuel port includes a second fuel port 1522.
  • the second fuel port 1522 may be formed through the tube 1520 and is disposed between the plurality of swirling guides 1531.
  • the second fuel port 1522 may be formed on an inner wall of the tube 1520 between the plurality of swirling guides 1531.
  • the second fuel port 1522 communicates with the fuel flow path 1513 of the fuel plenum 1510 and communicates with the inside of the tube 1520.
  • the second fuel port 1522 may inject the fuel between the swirling guides 1531. Accordingly, the fuel injected from the second fuel port 1522 is directly injected into the portion where the swirling flow is formed at the swirler 1530, so that the mixing characteristics of air and fuel can be improved.
  • the second fuel port 1522 may be disposed between the plurality of straight parts 1532, and/or between the plurality of swirling parts 1533.
  • the plurality of second fuel ports 1522 may be disposed between the plurality of straight parts 1532 and/or between the plurality of swirling parts 1533.
  • FIG. 8 is a longitudinal-sectional view separately illustrating a tube and a swirler of a nozzle according to a third embodiment of the present invention in an enlarged fashion.
  • a combustor nozzle 1220 according to a third embodiment of the present invention will be described in detail with reference to FIG. 8 . Since the combustor nozzle 1220 according to the third embodiment of the present invention is the same as the combustor nozzle 1220 according to the first embodiment of the present invention, except for a third fuel port 1523, a redundant description thereof will be omitted.
  • the fuel port includes the third fuel port 1523.
  • the third fuel port 1523 may be disposed in front of the swirler 1530.
  • an area in which the third fuel port 1523 is disposed is required to be between the front end of the tube 1520 and the front of the swirler 1530, so the third embodiment of the present invention may be applied when the swirler 1530 is disposed so as to be spaced apart from the front end of the tube 1520.
  • the swirler 1530 is preferably disposed closer to the front side of the tube 1520 than the rear end side of the tube 1520. That is, it is preferred that the swirler 1530 is spaced apart from the front end of the tube 1520 by a small gap, in which the third fuel port is disposed.
  • the gap may be formed to be smaller than the axial length of the swirler 1530. Accordingly, even when the third fuel port 1523 is disposed, the length of the tube 1520 can be minimized.
  • the third fuel port 1523 is formed to pass through the tube 1520 and communicates with the fuel flow path 1513 of the fuel plenum 1510 so that the third fuel port communicates with the interior of the tube 1520. Accordingly, the third fuel port 1523 may inject the fuel in the fuel flow path 1513 toward the front side before the swirler 1530. In this case, before air passes through the swirler 1530, the fuel may be injected into the air, so the air and the fuel may be mixed in advance in front of the swirler 1530. Accordingly, after being mixed in advance, the air and the fuel are mixed once again while passing through the swirler 1530, so the degree of mixing of the air and the fuel can be improved.
  • FIG. 9 is a longitudinal-sectional view separately illustrating a tube and a swirler of a nozzle according to a fourth embodiment of the present invention in an enlarged fashion.
  • a combustor nozzle 1220 according to a fourth embodiment of the present invention will be described in detail with reference to FIG. 9 . Since the combustor nozzle 1220 according to the fourth embodiment of the present invention is the same as the combustor nozzle 1220 according to the first embodiment of the present invention, except for a fourth fuel port 1524, a redundant description thereof will be omitted.
  • the fuel port includes the fourth fuel port 1524.
  • the fourth fuel port 1524 may be disposed at the rear side of the swirler 1530. Since the fourth fuel port 1524 is disposed at the rear side of the swirler 1530, unlike the third embodiment of the present invention, the swirler 1530 may be disposed at the front end terminal of the tube 1520.
  • the fourth fuel port 1524 is preferably disposed at a position close to the swirler 1530, while still being disposed behind the swirler 1530. Otherwise, if the fourth fuel port is separated away from the swirler 1524, the mixing degree of air and fuel may deteriorate. According to an embodiment, a gap between the fourth fuel port 1524 and the swirler 1530 may be formed to be smaller than the axial length of the swirler 1530.
  • the fourth fuel port 1524 is formed through the tube 1520 and communicates with the fuel flow path 1513 of the fuel plenum 1510 so that the fourth fuel port communicates with the interior of the tube 1520. Accordingly, the fourth fuel port 1524 may inject fuel in the fuel flow path 1513 toward the rear side of the swirler 1530. In this case, since fuel can be additionally injected from the rear side of the swirler 1530, there is an advantage in that a ratio of fuel in the air-fuel mixture can be further increased.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Pre-Mixing And Non-Premixing Gas Burner (AREA)
  • Tires In General (AREA)

Claims (15)

  1. Brennerdüse (1220), umfassend ein Düsenmodul (1400), wobei das Düsenmodul (1400) umfasst:
    ein Brennstoffzufuhrrohr (1420), das Brennstoff von einer vorderen Seite zu einer rückwärtigen Seite zuführt;
    eine Brennstoffkammer (1510) mit einem internen Brennstoffströmungspfad, durch den der Brennstoff strömt und der mit dem Brennstoffzufuhrrohr (1420) kommuniziert;
    einen Lufteinlass (1511), der an einem vorderen Ende der Brennstoffkammer (1510) gebildet ist;
    eine Mehrzahl von Rohren (1520), die durch eine rückwärtige Seite der Brennstoffkammer (1510) eingerichtet sind, wobei ein vorderes Ende jedes Rohrs (1520) mit dem Lufteinlass (1511) kommuniziert, und wobei ein Brennstoffanschluss, der mit dem Brennstoffströmungspfad kommuniziert, an einer seitlichen Seite jedes Rohrs (1520) gebildet ist; und
    einen Verwirbeler (1530), der mit einer Mehrzahl von verwirbelnden Führungen (1531) bereitgestellt ist, die schräg in axialen- und umfänglichen Richtungen auf einer inneren umfänglichen Oberfläche jedes der Mehrzahl von Rohren (1520) eingerichtet sind, um Fluid zu verwirbeln, mit einem zentralen Abschnitt (1530a) davon, der bei Betrachtung von der axialen Richtung des Rohrs (1520) geöffnet ist,
    dadurch gekennzeichnet, dass jede von der Mehrzahl von verwirbelnden Führungen (1531) einen geraden Teil (1532), der sich entlang der axialen Richtung des Rohrs (1520) erstreckt, und einen verwirbelnden Teil (1533), der sich in den axialen und umfänglichen Richtungen des Rohrs (1520) von einem hinteren Ende des geraden Teils (1532) erstreckt, beinhaltet.
  2. Brennerdüse (1220) nach Anspruch 1, wobei der Verwirbeler (1530) den zentralen Abschnitt (1530a) bei Betrachtung von der axialen Richtung des Rohrs (1520) in einer kreisförmigen Form geöffnet hat.
  3. Brennerdüse (1220) nach Anspruch 1, wobei die Mehrzahl von verwirbelnden Führungen (1531) bei Betrachtung von der axialen Richtung des Rohrs in einer kontinuierlichen kreisförmigen Form eingerichtet ist.
  4. Brennerdüse (1220) nach einem der vorhergehenden Ansprüche, wobei der verwirbelnde Teil (1533) gebildet ist, um in einer gekrümmten Form an dem Rohr (1520) geneigt zu sein.
  5. Brennerdüse (1220) nach einem der vorhergehenden Ansprüche, wobei die Länge des verwirbelnden Teils (1533) in der axialen Richtung des Rohrs (1520) länger gebildet ist als die des geraden Teils (1532).
  6. Brennerdüse (1220) nach einem der vorhergehenden Ansprüche, wobei ein vorderes Ende des geraden Teils (1532) mit einem geneigten Abschnitt (1534) bereitgestellt ist, der zu der rückwärtigen Seite hin geneigt ist, sowie sich der geneigte Abschnitt (1534) von der äußeren Seite hin zu der inneren Seite des Rohrs (1520) erstreckt.
  7. Brennerdüse (1220) nach Anspruch 1, wobei der Brennstoffanschluss einen ersten Brennstoffanschluss (1521) beinhaltet, der durch das Rohr (1520) und die Mehrzahl von verwirbelnden Führungen (1531) hindurchgeht und an der Mehrzahl von verwirbelnden Führungen (1531) eingerichtet ist.
  8. Brennerdüse (1220) nach einem der Ansprüche 1 bis 3, wobei der Brennstoffanschluss einen ersten Brennstoffanschluss (1521) beinhaltet, der durch das Rohr (1520) und die Mehrzahl von verwirbelnden Führungen (1531) hindurchgeht und auf dem geraden Teil (1532) eingerichtet ist.
  9. Brennerdüse (1220) nach Anspruch 1, wobei der Brennstoffanschluss einen zweiten Brennstoffanschluss (1522) beinhaltet, der durch das Rohr (1520) hindurchgeht und zwischen der Mehrzahl von verwirbelnden Führungen (1531) eingerichtet ist.
  10. Brennerdüse (1220) nach einem der Ansprüche 1 bis 3, wobei der Brennstoffanschluss einen zweiten Brennstoffanschluss (1522) beinhaltet, der durch das Rohr (1520) hindurchgeht und zwischen den geraden Teilen (1532) eingerichtet ist.
  11. Brennerdüse (1220) nach einem der Ansprüche 1 bis 3, wobei der Brennstoffanschluss einen zweiten Brennstoffanschluss (1522) beinhaltet, der durch das Rohr (1520) hindurchgeht und zwischen der Mehrzahl von verwirbelnden Teilen (1533) eingerichtet ist.
  12. Brennerdüse (1220) nach Anspruch 1, wobei der Verwirbeler (1530) an dem vorderen Ende des Rohrs (1520) eingerichtet ist.
  13. Brennerdüse (1220) nach Anspruch 1, wobei der Brennstoffanschluss einen dritten Brennstoffanschluss (1523) beinhaltet, der durch das Rohr (1520) hindurchgeht und an einer vorderen Seite des Verwirbelers (1530) eingerichtet ist.
  14. Brennerdüse (1220) nach Anspruch 1, wobei der Brennstoffanschluss einen vierten Brennstoffanschluss (1524) beinhaltet, der durch das Rohr (1520) hindurchgeht und an einer rückwärtigen Seite des Verwirbelers (1530) eingerichtet ist.
  15. Brenner (1200), welcher beinhaltet:
    eine Brennerdüse (1220) in Übereinstimmung mit Anspruch 1; und
    eine Führungsanordnung (1240), die mit einer Seite der Brennerdüse (1220) gekoppelt ist, wobei die Führungsanordnung (1240) zum Verbrennen von Brennstoff und Luft darin und zum Zuführen der Verbrennungsgase zu einer Turbine (1300) ausgebildet ist.
EP23150043.0A 2022-01-18 2023-01-02 Brennkammerdüse Active EP4212777B1 (de)

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KR1020220007492A KR102663869B1 (ko) 2022-01-18 2022-01-18 연소기용 노즐, 연소기 및 이를 포함하는 가스 터빈

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KR102663869B1 (ko) 2024-05-03
JP2023104876A (ja) 2023-07-28
KR20230111530A (ko) 2023-07-25
KR20240067858A (ko) 2024-05-17
EP4212777A1 (de) 2023-07-19
US11815266B2 (en) 2023-11-14
US20230228423A1 (en) 2023-07-20
JP7524509B2 (ja) 2024-07-30

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